Airworthiness Directives; Airbus Airplanes, 24039-24043 [2017-10282]

Download as PDF Federal Register / Vol. 82, No. 100 / Thursday, May 25, 2017 / Rules and Regulations Issued in Renton, Washington, on May 10, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–10266 Filed 5–24–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–8849; Directorate Identifier 2015–NM–174–AD; Amendment 39–18892; AD 2017–10–18] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for all Airbus Model A330–223F, –223, –321, –322, and –323 airplanes. This AD was prompted by fatigue load analysis that determined the need for reduced inspection intervals and updated torque values of the bolts. This AD requires repetitive torque checks of the forward engine mount bolts, an inspection of the forward mount assembly, and replacement of the bolts or repair of the forward mount assembly as necessary. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective June 29, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of June 29, 2017. ADDRESSES: For service information identified in this final rule, contact Airbus SAS, Airworthiness Office— EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@ airbus.com; Internet https:// www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227– 1221. It is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2016–8849. SUMMARY: VerDate Sep<11>2014 15:57 May 24, 2017 Jkt 241001 Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 8849; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (telephone 800–647–5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone: 425–227–1138; fax: 425–227–1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all Airbus Model A330–223F, –223, –321, –322, and –323 airplanes. The NPRM published in the Federal Register on August 30, 2016 (81 FR 59535). The NPRM was prompted by fatigue load analysis that determined the need for reduced inspection intervals (for torque checks required by AD 2013–14–04, Amendment 39–17509 (78 FR 68352, November 14, 2013) (‘‘AD 2013–14–04’’)) and updated torque values of the bolts. The NPRM proposed to require repetitive torque checks to determine if there are any loose or broken forward engine mount bolts, and, if necessary, replacement of all four forward engine mount bolts and associated nuts, inspection of the forward mount assembly, and repair. We are issuing this AD to detect and correct loose and broken bolts, which could lead to engine detachment in flight and damage to the airplane. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2015–0214, dated October 19, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus Model A330–223F, –223, –321, –322, and –323 airplanes. The MCAI states: The forward mount engine pylon bolts, Part Number (P/N) 51U615, fitted on Airbus PO 00000 Frm 00041 Fmt 4700 Sfmt 4700 24039 A330 aeroplanes with Pratt & Whitney (PW) PW4000 engines, are made from MP159 material. Analysis made by PW identified that MP159 material pylon bolts do not meet the full life cycle torque check interval requirement, in a bolt-out condition. Consequently, PW issued Alert Service Bulletin (ASB) PW4G–100–A71–32, and the U.S. Federal Aviation Administration (FAA), as Engine Certification Authority, issued FAA AD 2006–16–05 [Amendment 39–14705 (71 FR 44185, August 4, 2006) (‘‘AD 2006– 16–05’’)] to require repetitive torque checks of MP159 material forward mount pylon bolts fitted on certain PW4000 series engines. However, the engine mount system is considered to be part of aeroplane certification rather than the engine certification. Following further fatigue load analysis by Airbus of the A330 engine mount system, it was determined that the torque check interval for MP159 material forward mount pylon bolts, as required by FAA AD 2006–16–05 (2,700 flight cycles (FC)), provided an insufficient level of safety for Airbus A330 aeroplanes. This condition, if not detected and corrected, could ultimately lead to detachment of the engine from the aeroplane, possibly resulting in damage to the aeroplane and/or injury to persons on the ground. Consequently, EASA issued AD 2012–0094 [which corresponds to FAA AD 2013–14–04] to require accomplishment of repetitive torque checks of the forward mount pylon bolts installed on affected A330 aeroplanes and, depending on findings, replacement of all four bolts and associated nuts, in accordance with PW ASB PW4G–100–A71– 32 Revision 01 and Airbus Service Bulletin (SB) A330–71–3028. Since that AD was issued, it has been concluded that a new torque value must be applied. Consequently, Airbus issued SB A330–71– 3028 Revision 02 and PW issued ASB PW4G–100–A71–32 Revision 02 to update the torque value. Additional forward mount inspections are also provided in case of one or more forward engine mount bolts is found loose, broken or missing. For the reasons described above, this [EASA] AD retains the requirements of EASA AD 2012–0094, which is superseded, introduces a new torque value, and requires additional inspections and, depending on findings, corrective action(s). Corrective actions include repetitive torque checks to determine if there are any loose or broken forward engine mount bolts on both engines, and, if necessary, replacement of all four forward engine mount bolts and associated nuts, inspection of the forward mount assembly, and repair. You may examine the MCAI in the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 8849. Comments We gave the public the opportunity to participate in developing this AD. The E:\FR\FM\25MYR1.SGM 25MYR1 24040 Federal Register / Vol. 82, No. 100 / Thursday, May 25, 2017 / Rules and Regulations Request To Allow Use of Higher Torque Values following presents the comments received on the NPRM and the FAA’s response to each comment. Request To Correct Typographical Error American Airlines (AA) requested that we correct the reference to the FAA AD in paragraph (g)(1) of the proposed AD, which incorrectly identified AD 2013–13–05. The correct AD number for this terminating action is 2013–14–04. We agree and have revised paragraph (g)(1) of this AD accordingly. Request To Clarify Compliance Time AA requested that we clarify the compliance time for airplanes with an average flight time (AFT) of more than 132 minutes for the second cycle interval (1,851–2,700 flight cycles). AA proposed that we revise the second row of table 1 to paragraph (g) of the proposed AD by referring to the specified compliance times since accomplishing actions in AD 2013–14– 04. We agree that clarification is necessary. The compliance times for the initial and repetitive torque checks required by AD 2013–14–04 are identified in table 1 to paragraph (g)(1) of this AD (table 1 to paragraph (g) of the proposed AD). The compliance times include specified flight cycles since the last torque check specified in Pratt & Whitney Alert Service Bulletin PW4G–100–A71–32, which operators might have accomplished to comply with AD 2013–14–04. Paragraph (g)(1) of this AD requires that the next torque check be done in accordance with Airbus Service Bulletin A330–71–3028, Revision 02, dated August 31, 2015 (‘‘A330–71–3028, R02’’). Accomplishment of the torque check required by paragraph (g)(1) of this AD terminates the requirements of AD 2013–14–04. We have not changed this AD regarding this issue. Request To Clarify Terminating Action Paragraph (h) of the proposed AD stated that accomplishment of the actions specified by paragraph (g) of the proposed AD ‘‘constitutes compliance with’’ the requirements specified in paragraph (g) of AD 2006–16–05. AA requested that we revise paragraph (h) of the proposed AD to specifically state that the new AD would also ‘‘terminate’’ the inspection specified in AD 2006– 16–05. We agree with the commenter. We have revised paragraph (h) of this AD to state that accomplishment of the actions required by paragraph (g) of this AD terminates the requirements of paragraph (g) of AD 2006–16–05. VerDate Sep<11>2014 15:57 May 24, 2017 Jkt 241001 AA requested that we revise paragraph (j) of the proposed AD to specifically allow early compliance with the AD upon its release and prior to the effective date of the AD, using Airbus Service Bulletin A330–71–3028, R02. AA stated that this would allow operators to immediately begin using the higher torque values specified in Airbus Service Bulletin A330–71–3028, R02. AA stated that as written, the AD would not allow operators to immediately use the higher torque values specified in Airbus Service Bulletin A330–71–3028, R02, because AD 2013–14–04 specifies the use of Airbus Service Bulletin A330–71–3028, Revision 01, dated February 12, 2012, which contains lower torque values. AA stated that this would preclude the need for a request for an alternative method of compliance (AMOC) against AD 2013–14–04 to allow the use of the higher torque values, and that this change would streamline the compliance revision process. We acknowledge the request and agree that clarification is necessary. Because AD 2013–14–04 requires using Airbus Service Bulletin A330–71–3028, Revision 01, dated February 12, 2012, operators need approval to use Airbus Service Bulletin A330–71–3028, R02, as an AMOC for the requirements of AD 2013–14–04. We have issued global AMOC ANM–116–17–243, dated April 4, 2017, approving the use of Airbus Service Bulletin A330–71–3028, R02, for compliance with the requirements of AD 2013–14–04. Therefore, no changes to this AD are necessary regarding this issue. Request To Limit Requirements for Certain Approvals Delta Air Lines (Delta) requested that we revise the statement in paragraph (g)(2) of the proposed AD to remove the requirement to obtain FAA, EASA, or Airbus Design Organization Approval (DOA) approval for any instance where Airbus Service Bulletin A330–71–3028, R02, specifies contacting Airbus. Delta requested that we instead require these approvals only for damage that exceeds the allowable limits in the airplane maintenance manual (AMM); component maintenance manual (CMM); or cleaning, instruction and repair (CIR) manual. Delta stated that Airbus Service Bulletin A330–71–3028, R02, specifies contacting Airbus any time a bolt is found out of tolerance regardless whether any damage is found. As such, this would effectively require FAA, EASA, or Airbus DOA PO 00000 Frm 00042 Fmt 4700 Sfmt 4700 approval any time a bolt is found with a torque out of limits, even if there is no damage to the forward mount assembly, or if the damage is within the AMM, CMM, or CIR allowable limits. Delta agreed with the required approvals, but only when there is damage that exceeds those limits. Delta stated that this change would limit the number of AMOC requests, and reduce airplane out-of-service times while maintaining the acceptable level of safety. We disagree with the commenter’s request to change the corrective action requirement in paragraph (g)(2) of this AD. The requirements of this AD correspond with those specified in the MCAI. The MCAI refers to Airbus Service Bulletin A330–71–3028, R02, which specifies that when any bolt is found with a torque out of limits, corrective actions must be done. We have determined that these actions are necessary to address the identified unsafe condition. However, under the provisions of paragraph (k)(1) of this AD, we will consider requests for approval of alternative corrective actions if sufficient data are submitted to substantiate that the alternative actions would provide an acceptable level of safety. We have not changed this AD regarding this issue. Request To Allow Replacement Instead of Repair Delta stated that paragraph (g)(2) of the proposed AD, which applies to the airplane (not the engine mount), would require repair before further flight. Delta interpreted this to mean the proposed AD would require repair of the forward engine mount before the airplane could return to flight. Delta requested that we revise the proposed AD to include a statement that explicitly allows replacement of damaged engine mounts, allowing the airplane to return to service as quickly as possible. We partially agree with the commenter’s request. We agree that replacement of an affected forward engine mount might be allowed as a corrective action and that a different compliance time may be acceptable. We have revised paragraph (g)(2) of this AD by replacing the proposed requirement to repair before further flight with the requirement to contact the FAA, EASA, or Airbus’s EASA DOA before further flight to obtain applicable corrective action instructions approved by the FAA, EASA, or Airbus’s EASA DOA, and to do applicable corrective actions within the compliance time specified in those instructions. E:\FR\FM\25MYR1.SGM 25MYR1 Federal Register / Vol. 82, No. 100 / Thursday, May 25, 2017 / Rules and Regulations Conclusion We reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these changes: • Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A330–71–3028, Revision 02, dated August 31, 2015. The service information describes procedures for repetitive torque checks for loose or broken forward engine mount bolts on both engines, replacement of all four forward engine mount bolts and associated nuts, and inspection of the forward mount assembly. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Costs of Compliance We estimate that this AD affects 41 airplanes of U.S. registry. We also estimate that it would take about 3 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Required parts would cost about $6,747 per product. Based on these figures, we estimate the cost of this AD on U.S. operators to be $287,082, or $7,002 per product. In addition, we estimate that any necessary follow-on actions would take about 1 work-hour and require parts costing $6,747, for a cost of $6,832 per product. We have no way of determining the number of aircraft that might need these actions. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of VerDate Sep<11>2014 15:57 May 24, 2017 Jkt 241001 the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. PO 00000 Frm 00043 Fmt 4700 Sfmt 4700 § 39.13 24041 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2017–10–18 Airbus: Amendment 39–18892; Docket No. FAA–2016–8849; Directorate Identifier 2015–NM–174–AD. (a) Effective Date This AD is effective June 29, 2017. (b) Affected ADs This AD affects AD 2006–16–05, Amendment 39–14705 (71 FR 44185, August 4, 2006) (‘‘AD 2006–16–05’’); and AD 2013– 14–04, Amendment 39–17509 (78 FR 68352, November 14, 2013) (‘‘AD 2013–14–04’’). (c) Applicability This AD applies to Airbus Model A330– 223F, –223, –321, –322, and –323 airplanes, certificated in any category, all manufacturer serial numbers. (d) Subject Air Transport Association (ATA) of America Code 71, Powerplant. (e) Reason This AD was prompted by fatigue load analysis that determined the need for certain reduced inspection intervals and updated torque values of the forward engine mount pylon bolts. We are issuing this AD to detect and correct loose or broken bolts, which could lead to engine detachment in flight and damage to the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Torque Check, Replacement, and Terminating Action for AD 2013–14–04 (1) At the applicable compliance time specified in table 1 to paragraph (g)(1) of this AD, do a torque check to determine if there are any loose or broken forward engine mount bolts (4 positions/engine) on both engines, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–71–3028, Revision 02, dated August 31, 2015. Repeat the torque check at the applicable time intervals not to exceed the values specified in table 1 to paragraph (g)(1) of this AD. For the purposes of this AD, the average flight time (AFT) is defined as a computation of the number of flight hours divided by the number of flight cycles accumulated since the most recent torque check or since the airplane’s first flight, as applicable. Accomplishment of the initial torque check required by this paragraph terminates the requirements of AD 2013–14–04. E:\FR\FM\25MYR1.SGM 25MYR1 24042 Federal Register / Vol. 82, No. 100 / Thursday, May 25, 2017 / Rules and Regulations TABLE 1 TO PARAGRAPH (g)(1) OF THIS AD Flight cycles accumulated as of December 19, 2013 (the effective date of AD 2013–14– 04), since last torque check specified in Pratt & Whitney Alert Service Bulletin PW4G–100– A71–32 or since airplane’s first flight, as applicable Airplane models Model A330–321, –322, and –323 airplanes with AFT more than 132 minutes; and Model A330–223 airplanes. 0–1,850 Model A330–321, –322, and –323 airplanes with AFT more than 132 minutes; and Model A330–223 airplanes. 1,851–2,700 Model A330–321, –322, and –323 airplanes with AFT 132 minutes or less; and Model A330–321, –322, and –323 airplanes on which the AFT is not calculated on a regular basis. Model A330–321, –322, and –323 airplanes with AFT 132 minutes or less; and Model A330–321, –322, and -323 airplanes on which the AFT is not calculated on a regular basis. 0–1,450 1,451–2,700 Model A330–223F airplanes .......................... Any (2) If any loose or broken bolt is detected during the check required by paragraph (g)(1) of this AD, before further flight, do the actions specified by paragraphs (g)(2)(i) and (g)(2)(ii) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–71–3028, Revision 02, dated August 31, 2015; except, where the service information specifies to contact the manufacturer for further corrective actions, before further flight contact the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA); to obtain applicable corrective action instructions approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or EASA; or Airbus’s EASA DOA; and accomplish the applicable corrective actions within the compliance time specified in those instructions. (i) Replace all four forward engine mount bolts and associated nuts, on the engine where the loose or broken bolt was detected, with new bolts and nuts. (ii) Do nondestructive inspections of the forward mount assembly for damage including cracks, dents, nicks, and scratches, and do all applicable corrective actions. VerDate Sep<11>2014 15:57 May 24, 2017 Jkt 241001 Compliance time Torque check interval (not to exceed) Within 2,350 flight cycles since the last torque check as specified in Pratt & Whitney Alert Service Bulletin PW4G–100– A71–32, or since airplane’s first flight, as applicable. Within 500 flight cycles after December 19, 2013 (the effective date of AD 2013–14– 04), without exceeding 2,700 flight cycles since last torque check as specified in Pratt & Whitney Alert Service Bulletin PW4G–100–A71–32, or since airplane’s first flight, as applicable; or within 3 months after December 19, 2013; whichever occurs later. Within 1,950 flight cycles since the last torque check performed as specified in Pratt & Whitney Alert Service Bulletin PW4G–100–A71–32, or since airplane’s first flight, as applicable. Within 500 flight cycles after December 19, 2013 (the effective date of AD 2013–14– 04), without exceeding 2,700 flight cycles since last torque check performed as specified in Pratt & Whitney Alert Service Bulletin PW4–100–A71–32, or since airplane’s first flight, as applicable; or within 3 months after December 19, 2013; whichever occurs later. Within 2,140 flight cycles or 6,600 flight hours, whichever occurs first since the last torque check performed as specified in Pratt & Whitney Alert Service Bulletin PW4G–100–A71–32, or since airplane’s first flight, as applicable. 2,350 flight cycles or 24,320 flight hours, whichever occurs first. (3) Replacement of bolts and nuts as required by paragraph (g)(2)(i) of this AD is not terminating action for the repetitive torque checks required by paragraph (g)(1) of this AD. (h) Terminating Action for Paragraph (g) of AD 2006–16–05 Accomplishment of the actions required by paragraph (g) of this AD terminates the requirements specified in paragraph (g) of AD 2006–16–05. (i) Parts Installation Prohibition As of December 19, 2013 (the effective date of AD 2013–14–04), no person may install, on any airplane, any forward mount pylon bolt made of INCO718 material and having Pratt & Whitney part number 54T670. (j) Credit for Previous Actions This paragraph provides credit for the actions required by paragraphs (g)(1) and (g)(2)(i) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A330–71–3028, dated December 16, 2011, or Airbus Service Bulletin A330–71–3028, Revision 01, dated February 20, 2012. PO 00000 Frm 00044 Fmt 4700 Sfmt 4700 2,350 flight cycles or 24,320 flight hours, whichever occurs first. 1,950 flight cycles or 20,210 flight hours, whichever occurs first. 1,950 flight cycles or 20,210 flight hours, whichever occurs first. 2,140 flight cycles or 6,600 flight hours, whichever occurs first. (k) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone: 425–227–1138; fax: 425–227– 1149. Information may be emailed to: 9ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (2) Contacting the Manufacturer: As of the effective date of this AD, for any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by E:\FR\FM\25MYR1.SGM 25MYR1 Federal Register / Vol. 82, No. 100 / Thursday, May 25, 2017 / Rules and Regulations the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): Except as required by paragraph (g)(2) of this AD: If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (l) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2015–0214, dated October 19, 2015, for related information. This MCAI may be found in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2016–8849. (2) For more information about this AD, contact Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone: 425–227–1138; fax: 425–227– 1149. (3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (m)(3) and (m)(4) of this AD. (m) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Airbus Service Bulletin A330–71–3028, Revision 02, dated August 31, 2015. (ii) Reserved. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; Internet https://www.airbus.com. (4) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to https:// www.archives.gov/federal-register/cfr/ibrlocations.html. VerDate Sep<11>2014 15:57 May 24, 2017 Jkt 241001 Issued in Renton, Washington, on May 8, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–10282 Filed 5–24–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–9431; Directorate Identifier 2016–NM–104–AD; Amendment 39–18897; AD 2017–10–23] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: 24043 and locating Docket No. FAA–2016– 9431; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone 800–647– 5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; fax 425–227–1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would SUMMARY: We are adopting a new apply to certain Airbus Model A321 airworthiness directive (AD) for certain series airplanes. The NPRM published Airbus Model A321 series airplanes. in the Federal Register on December 2, This AD was prompted by a determination that cracks could develop 2016 (81 FR 86975). The NPRM was prompted by a determination from on holes at certain fuselage frame fatigue testing on the Model A321 locations. This AD requires repetitive airframe that cracks could develop on inspections for cracking on holes at holes at certain fuselage frame locations. certain fuselage frame locations, and The NPRM proposed to require repairs if necessary. We are issuing this repetitive inspections for cracking on AD to address the unsafe condition on holes at certain fuselage frame locations, these products. and repairs if necessary. We are issuing DATES: This AD is effective June 29, this AD to detect and correct cracking at 2017. certain hole locations in the fuselage The Director of the Federal Register approved the incorporation by reference frame, which could result in reduced structural integrity of the airplane. of certain publications listed in this AD The European Aviation Safety Agency as of June 29, 2017. (EASA), which is the Technical Agent ADDRESSES: For service information for the Member States of the European identified in this final rule, contact Union, has issued EASA Airworthiness Airbus, Airworthiness Office—EIAS, 1 Directive 2016–0106, dated June 6, 2016 Rond Point Maurice Bellonte, 31707 (referred to after this as the Mandatory Blagnac Cedex, France; telephone +33 5 Continuing Airworthiness Information, 61 93 36 96; fax +33 5 61 93 44 51; email or ‘‘the MCAI’’), to correct an unsafe account.airworth-eas@airbus.com; condition on certain Airbus Model A321 Internet https://www.airbus.com. You series airplanes. The MCAI states: may view this referenced service Following a new full scale fatigue test information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue campaign on the A321 airframe, in the context of the A321 extended service goal, it SW., Renton, WA. For information on was identified that cracks could develop on the availability of this material at the holes at frame (FR) 35.2A between stringers FAA, call 425–227–1221. It is also (STR) 22 and STR 23 on right hand (RH) and left hand (LH) sides, also on aeroplanes available on the Internet at https:// operated in the context of design service goal. www.regulations.gov by searching for This condition, if not detected and and locating Docket No. FAA–2016– corrected, could reduce the structural 9431. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for PO 00000 Frm 00045 Fmt 4700 Sfmt 4700 integrity of the fuselage. Prompted by these findings, Airbus developed an inspection programme, published in Service Bulletin (SB) A320–53– 1315 and SB A320–53–1316, each containing instructions for a different location. E:\FR\FM\25MYR1.SGM 25MYR1

Agencies

[Federal Register Volume 82, Number 100 (Thursday, May 25, 2017)]
[Rules and Regulations]
[Pages 24039-24043]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-10282]

-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-8849; Directorate Identifier 2015-NM-174-AD;
Amendment 39-18892; AD 2017-10-18]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for all
Airbus Model A330-223F, -223, -321, -322, and -323 airplanes. This AD
was prompted by fatigue load analysis that determined the need for
reduced inspection intervals and updated torque values of the bolts.
This AD requires repetitive torque checks of the forward engine mount
bolts, an inspection of the forward mount assembly, and replacement of
the bolts or repair of the forward mount assembly as necessary. We are
issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective June 29, 2017.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of June 29,
2017.

ADDRESSES: For service information identified in this final rule,
contact Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax
+33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; Internet
https://www.airbus.com. You may view this referenced service information
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information on the availability of this material at the
FAA, call 425-227-1221. It is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
8849.

Examining the AD Docket

You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
8849; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this AD, the regulatory evaluation, any comments received, and
other information. The address for the Docket Office (telephone 800-
647-5527) is Docket Management Facility, U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-227-1138;
fax: 425-227-1149.

SUPPLEMENTARY INFORMATION:

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to all Airbus Model A330-223F,
-223, -321, -322, and -323 airplanes. The NPRM published in the Federal
Register on August 30, 2016 (81 FR 59535). The NPRM was prompted by
fatigue load analysis that determined the need for reduced inspection
intervals (for torque checks required by AD 2013-14-04, Amendment 39-
17509 (78 FR 68352, November 14, 2013) (``AD 2013-14-04'')) and updated
torque values of the bolts. The NPRM proposed to require repetitive
torque checks to determine if there are any loose or broken forward
engine mount bolts, and, if necessary, replacement of all four forward
engine mount bolts and associated nuts, inspection of the forward mount
assembly, and repair. We are issuing this AD to detect and correct
loose and broken bolts, which could lead to engine detachment in flight
and damage to the airplane.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2015-0214, dated October 19, 2015 (referred to after this as the
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to
correct an unsafe condition for all Airbus Model A330-223F, -223, -321,
-322, and -323 airplanes. The MCAI states:

The forward mount engine pylon bolts, Part Number (P/N) 51U615,
fitted on Airbus A330 aeroplanes with Pratt & Whitney (PW) PW4000
engines, are made from MP159 material. Analysis made by PW
identified that MP159 material pylon bolts do not meet the full life
cycle torque check interval requirement, in a bolt-out condition.
Consequently, PW issued Alert Service Bulletin (ASB) PW4G-100-A71-
32, and the U.S. Federal Aviation Administration (FAA), as Engine
Certification Authority, issued FAA AD 2006-16-05 [Amendment 39-
14705 (71 FR 44185, August 4, 2006) (``AD 2006-16-05'')] to require
repetitive torque checks of MP159 material forward mount pylon bolts
fitted on certain PW4000 series engines.
However, the engine mount system is considered to be part of
aeroplane certification rather than the engine certification.
Following further fatigue load analysis by Airbus of the A330 engine
mount system, it was determined that the torque check interval for
MP159 material forward mount pylon bolts, as required by FAA AD
2006-16-05 (2,700 flight cycles (FC)), provided an insufficient
level of safety for Airbus A330 aeroplanes.
This condition, if not detected and corrected, could ultimately
lead to detachment of the engine from the aeroplane, possibly
resulting in damage to the aeroplane and/or injury to persons on the
ground.
Consequently, EASA issued AD 2012-0094 [which corresponds to FAA
AD 2013-14-04] to require accomplishment of repetitive torque checks
of the forward mount pylon bolts installed on affected A330
aeroplanes and, depending on findings, replacement of all four bolts
and associated nuts, in accordance with PW ASB PW4G-100-A71-32
Revision 01 and Airbus Service Bulletin (SB) A330-71-3028.
Since that AD was issued, it has been concluded that a new
torque value must be applied.
Consequently, Airbus issued SB A330-71-3028 Revision 02 and PW
issued ASB PW4G-100-A71-32 Revision 02 to update the torque value.
Additional forward mount inspections are also provided in case of
one or more forward engine mount bolts is found loose, broken or
missing.
For the reasons described above, this [EASA] AD retains the
requirements of EASA AD 2012-0094, which is superseded, introduces a
new torque value, and requires additional inspections and, depending
on findings, corrective action(s).

Corrective actions include repetitive torque checks to determine if
there are any loose or broken forward engine mount bolts on both
engines, and, if necessary, replacement of all four forward engine
mount bolts and associated nuts, inspection of the forward mount
assembly, and repair. You may examine the MCAI in the AD docket on the
Internet at https://www.regulations.gov by searching for and locating
Docket No. FAA-2016-8849.

Comments

We gave the public the opportunity to participate in developing
this AD. The

[[Page 24040]]

following presents the comments received on the NPRM and the FAA's
response to each comment.

Request To Correct Typographical Error

American Airlines (AA) requested that we correct the reference to
the FAA AD in paragraph (g)(1) of the proposed AD, which incorrectly
identified AD 2013-13-05. The correct AD number for this terminating
action is 2013-14-04.
We agree and have revised paragraph (g)(1) of this AD accordingly.

Request To Clarify Compliance Time

AA requested that we clarify the compliance time for airplanes with
an average flight time (AFT) of more than 132 minutes for the second
cycle interval (1,851-2,700 flight cycles). AA proposed that we revise
the second row of table 1 to paragraph (g) of the proposed AD by
referring to the specified compliance times since accomplishing actions
in AD 2013-14-04.
We agree that clarification is necessary. The compliance times for
the initial and repetitive torque checks required by AD 2013-14-04 are
identified in table 1 to paragraph (g)(1) of this AD (table 1 to
paragraph (g) of the proposed AD). The compliance times include
specified flight cycles since the last torque check specified in Pratt
& Whitney Alert Service Bulletin PW4G-100-A71-32, which operators might
have accomplished to comply with AD 2013-14-04. Paragraph (g)(1) of
this AD requires that the next torque check be done in accordance with
Airbus Service Bulletin A330-71-3028, Revision 02, dated August 31,
2015 (``A330-71-3028, R02''). Accomplishment of the torque check
required by paragraph (g)(1) of this AD terminates the requirements of
AD 2013-14-04. We have not changed this AD regarding this issue.

Request To Clarify Terminating Action

Paragraph (h) of the proposed AD stated that accomplishment of the
actions specified by paragraph (g) of the proposed AD ``constitutes
compliance with'' the requirements specified in paragraph (g) of AD
2006-16-05. AA requested that we revise paragraph (h) of the proposed
AD to specifically state that the new AD would also ``terminate'' the
inspection specified in AD 2006-16-05.
We agree with the commenter. We have revised paragraph (h) of this
AD to state that accomplishment of the actions required by paragraph
(g) of this AD terminates the requirements of paragraph (g) of AD 2006-
16-05.

Request To Allow Use of Higher Torque Values

AA requested that we revise paragraph (j) of the proposed AD to
specifically allow early compliance with the AD upon its release and
prior to the effective date of the AD, using Airbus Service Bulletin
A330-71-3028, R02. AA stated that this would allow operators to
immediately begin using the higher torque values specified in Airbus
Service Bulletin A330-71-3028, R02. AA stated that as written, the AD
would not allow operators to immediately use the higher torque values
specified in Airbus Service Bulletin A330-71-3028, R02, because AD
2013-14-04 specifies the use of Airbus Service Bulletin A330-71-3028,
Revision 01, dated February 12, 2012, which contains lower torque
values. AA stated that this would preclude the need for a request for
an alternative method of compliance (AMOC) against AD 2013-14-04 to
allow the use of the higher torque values, and that this change would
streamline the compliance revision process.
We acknowledge the request and agree that clarification is
necessary. Because AD 2013-14-04 requires using Airbus Service Bulletin
A330-71-3028, Revision 01, dated February 12, 2012, operators need
approval to use Airbus Service Bulletin A330-71-3028, R02, as an AMOC
for the requirements of AD 2013-14-04. We have issued global AMOC ANM-
116-17-243, dated April 4, 2017, approving the use of Airbus Service
Bulletin A330-71-3028, R02, for compliance with the requirements of AD
2013-14-04. Therefore, no changes to this AD are necessary regarding
this issue.

Request To Limit Requirements for Certain Approvals

Delta Air Lines (Delta) requested that we revise the statement in
paragraph (g)(2) of the proposed AD to remove the requirement to obtain
FAA, EASA, or Airbus Design Organization Approval (DOA) approval for
any instance where Airbus Service Bulletin A330-71-3028, R02, specifies
contacting Airbus. Delta requested that we instead require these
approvals only for damage that exceeds the allowable limits in the
airplane maintenance manual (AMM); component maintenance manual (CMM);
or cleaning, instruction and repair (CIR) manual. Delta stated that
Airbus Service Bulletin A330-71-3028, R02, specifies contacting Airbus
any time a bolt is found out of tolerance regardless whether any damage
is found. As such, this would effectively require FAA, EASA, or Airbus
DOA approval any time a bolt is found with a torque out of limits, even
if there is no damage to the forward mount assembly, or if the damage
is within the AMM, CMM, or CIR allowable limits. Delta agreed with the
required approvals, but only when there is damage that exceeds those
limits. Delta stated that this change would limit the number of AMOC
requests, and reduce airplane out-of-service times while maintaining
the acceptable level of safety.
We disagree with the commenter's request to change the corrective
action requirement in paragraph (g)(2) of this AD. The requirements of
this AD correspond with those specified in the MCAI. The MCAI refers to
Airbus Service Bulletin A330-71-3028, R02, which specifies that when
any bolt is found with a torque out of limits, corrective actions must
be done. We have determined that these actions are necessary to address
the identified unsafe condition. However, under the provisions of
paragraph (k)(1) of this AD, we will consider requests for approval of
alternative corrective actions if sufficient data are submitted to
substantiate that the alternative actions would provide an acceptable
level of safety. We have not changed this AD regarding this issue.

Request To Allow Replacement Instead of Repair

Delta stated that paragraph (g)(2) of the proposed AD, which
applies to the airplane (not the engine mount), would require repair
before further flight. Delta interpreted this to mean the proposed AD
would require repair of the forward engine mount before the airplane
could return to flight. Delta requested that we revise the proposed AD
to include a statement that explicitly allows replacement of damaged
engine mounts, allowing the airplane to return to service as quickly as
possible.
We partially agree with the commenter's request. We agree that
replacement of an affected forward engine mount might be allowed as a
corrective action and that a different compliance time may be
acceptable. We have revised paragraph (g)(2) of this AD by replacing
the proposed requirement to repair before further flight with the
requirement to contact the FAA, EASA, or Airbus's EASA DOA before
further flight to obtain applicable corrective action instructions
approved by the FAA, EASA, or Airbus's EASA DOA, and to do applicable
corrective actions within the compliance time specified in those
instructions.

[[Page 24041]]

Conclusion

We reviewed the available data, including the comments received,
and determined that air safety and the public interest require adopting
this AD with the changes described previously and minor editorial
changes. We have determined that these changes:
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

Airbus has issued Service Bulletin A330-71-3028, Revision 02, dated
August 31, 2015. The service information describes procedures for
repetitive torque checks for loose or broken forward engine mount bolts
on both engines, replacement of all four forward engine mount bolts and
associated nuts, and inspection of the forward mount assembly. This
service information is reasonably available because the interested
parties have access to it through their normal course of business or by
the means identified in the ADDRESSES section.

Costs of Compliance

We estimate that this AD affects 41 airplanes of U.S. registry.
We also estimate that it would take about 3 work-hours per product
to comply with the basic requirements of this AD. The average labor
rate is $85 per work-hour. Required parts would cost about $6,747 per
product. Based on these figures, we estimate the cost of this AD on
U.S. operators to be $287,082, or $7,002 per product.
In addition, we estimate that any necessary follow-on actions would
take about 1 work-hour and require parts costing $6,747, for a cost of
$6,832 per product. We have no way of determining the number of
aircraft that might need these actions.

Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.

Regulatory Findings

We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.

Adoption of the Amendment

Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

Sec. 39.13 [Amended]

0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):

2017-10-18 Airbus: Amendment 39-18892; Docket No. FAA-2016-8849;
Directorate Identifier 2015-NM-174-AD.

(a) Effective Date

This AD is effective June 29, 2017.

(b) Affected ADs

This AD affects AD 2006-16-05, Amendment 39-14705 (71 FR 44185,
August 4, 2006) (``AD 2006-16-05''); and AD 2013-14-04, Amendment
39-17509 (78 FR 68352, November 14, 2013) (``AD 2013-14-04'').

This AD applies to Airbus Model A330-223F, -223, -321, -322, and
-323 airplanes, certificated in any category, all manufacturer
serial numbers.

(d) Subject

Air Transport Association (ATA) of America Code 71, Powerplant.

(e) Reason

This AD was prompted by fatigue load analysis that determined
the need for certain reduced inspection intervals and updated torque
values of the forward engine mount pylon bolts. We are issuing this
AD to detect and correct loose or broken bolts, which could lead to
engine detachment in flight and damage to the airplane.

(f) Compliance

Comply with this AD within the compliance times specified,
unless already done.

(g) Torque Check, Replacement, and Terminating Action for AD 2013-14-04

(1) At the applicable compliance time specified in table 1 to
paragraph (g)(1) of this AD, do a torque check to determine if there
are any loose or broken forward engine mount bolts (4 positions/
engine) on both engines, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A330-71-3028, Revision 02,
dated August 31, 2015. Repeat the torque check at the applicable
time intervals not to exceed the values specified in table 1 to
paragraph (g)(1) of this AD. For the purposes of this AD, the
average flight time (AFT) is defined as a computation of the number
of flight hours divided by the number of flight cycles accumulated
since the most recent torque check or since the airplane's first
flight, as applicable. Accomplishment of the initial torque check
required by this paragraph terminates the requirements of AD 2013-
14-04.

[[Page 24042]]

Table 1 to Paragraph (g)(1) of This AD
----------------------------------------------------------------------------------------------------------------
Flight cycles
accumulated as of
December 19, 2013 (the
effective date of AD
2013-14-04), since last
Airplane models torque check specified Compliance time Torque check interval
in Pratt & Whitney (not to exceed)
Alert Service Bulletin
PW4G-100-A71-32 or
since airplane's first
flight, as applicable
----------------------------------------------------------------------------------------------------------------
Model A330-321, -322, and -323 0-1,850 Within 2,350 flight 2,350 flight cycles or
airplanes with AFT more than 132 cycles since the last 24,320 flight hours,
minutes; and Model A330-223 torque check as whichever occurs
airplanes. specified in Pratt & first.
Whitney Alert Service
Bulletin PW4G-100-A71-
32, or since
airplane's first
flight, as applicable.
Model A330-321, -322, and -323 1,851-2,700 Within 500 flight 2,350 flight cycles or
airplanes with AFT more than 132 cycles after December 24,320 flight hours,
minutes; and Model A330-223 19, 2013 (the whichever occurs
airplanes. effective date of AD first.
2013-14-04), without
exceeding 2,700 flight
cycles since last
torque check as
specified in Pratt &
Whitney Alert Service
Bulletin PW4G-100-A71-
32, or since
airplane's first
flight, as applicable;
or within 3 months
after December 19,
2013; whichever occurs
later.
Model A330-321, -322, and -323 0-1,450 Within 1,950 flight 1,950 flight cycles or
airplanes with AFT 132 minutes or cycles since the last 20,210 flight hours,
less; and Model A330-321, -322, and - torque check performed whichever occurs
323 airplanes on which the AFT is as specified in Pratt first.
not calculated on a regular basis. & Whitney Alert
Service Bulletin PW4G-
100-A71-32, or since
airplane's first
flight, as applicable.
Model A330-321, -322, and -323 1,451-2,700 Within 500 flight 1,950 flight cycles or
airplanes with AFT 132 minutes or cycles after December 20,210 flight hours,
less; and Model A330-321, -322, and 19, 2013 (the whichever occurs
[dash]323 airplanes on which the AFT effective date of AD first.
is not calculated on a regular basis. 2013-14-04), without
exceeding 2,700 flight
cycles since last
torque check performed
as specified in Pratt
& Whitney Alert
Service Bulletin PW4-
100-A71-32, or since
airplane's first
flight, as applicable;
or within 3 months
after December 19,
2013; whichever occurs
later.
Model A330-223F airplanes............ Any Within 2,140 flight 2,140 flight cycles or
cycles or 6,600 flight 6,600 flight hours,
hours, whichever whichever occurs
occurs first since the first.
last torque check
performed as specified
in Pratt & Whitney
Alert Service Bulletin
PW4G-100-A71-32, or
since airplane's first
flight, as applicable.
----------------------------------------------------------------------------------------------------------------

(2) If any loose or broken bolt is detected during the check
required by paragraph (g)(1) of this AD, before further flight, do
the actions specified by paragraphs (g)(2)(i) and (g)(2)(ii) of this
AD, in accordance with the Accomplishment Instructions of Airbus
Service Bulletin A330-71-3028, Revision 02, dated August 31, 2015;
except, where the service information specifies to contact the
manufacturer for further corrective actions, before further flight
contact the Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA; or the European Aviation Safety Agency
(EASA); or Airbus's EASA Design Organization Approval (DOA); to
obtain applicable corrective action instructions approved by the
Manager, International Branch, ANM-116, Transport Airplane
Directorate, FAA; or EASA; or Airbus's EASA DOA; and accomplish the
applicable corrective actions within the compliance time specified
in those instructions.
(i) Replace all four forward engine mount bolts and associated
nuts, on the engine where the loose or broken bolt was detected,
with new bolts and nuts.
(ii) Do nondestructive inspections of the forward mount assembly
for damage including cracks, dents, nicks, and scratches, and do all
applicable corrective actions.
(3) Replacement of bolts and nuts as required by paragraph
(g)(2)(i) of this AD is not terminating action for the repetitive
torque checks required by paragraph (g)(1) of this AD.

(h) Terminating Action for Paragraph (g) of AD 2006-16-05

Accomplishment of the actions required by paragraph (g) of this
AD terminates the requirements specified in paragraph (g) of AD
2006-16-05.

(i) Parts Installation Prohibition

As of December 19, 2013 (the effective date of AD 2013-14-04),
no person may install, on any airplane, any forward mount pylon bolt
made of INCO718 material and having Pratt & Whitney part number
54T670.

(j) Credit for Previous Actions

This paragraph provides credit for the actions required by
paragraphs (g)(1) and (g)(2)(i) of this AD, if those actions were
performed before the effective date of this AD using Airbus Service
Bulletin A330-71-3028, dated December 16, 2011, or Airbus Service
Bulletin A330-71-3028, Revision 01, dated February 20, 2012.

(k) Other FAA AD Provisions

The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the International Branch, send it to ATTN: Vladimir
Ulyanov, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton,
WA 98057-3356; telephone: 425-227-1138; fax: 425-227-1149.
Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov.
Before using any approved AMOC, notify your appropriate principal
inspector, or lacking a principal inspector, the manager of the
local flight standards district office/certificate holding district
office.
(2) Contacting the Manufacturer: As of the effective date of
this AD, for any requirement in this AD to obtain corrective actions
from a manufacturer, the action must be accomplished using a method
approved by

[[Page 24043]]

the Manager, International Branch, ANM-116, Transport Airplane
Directorate, FAA; or EASA; or Airbus's EASA DOA. If approved by the
DOA, the approval must include the DOA-authorized signature.
(3) Required for Compliance (RC): Except as required by
paragraph (g)(2) of this AD: If any service information contains
procedures or tests that are identified as RC, those procedures and
tests must be done to comply with this AD; any procedures or tests
that are not identified as RC are recommended. Those procedures and
tests that are not identified as RC may be deviated from using
accepted methods in accordance with the operator's maintenance or
inspection program without obtaining approval of an AMOC, provided
the procedures and tests identified as RC can be done and the
airplane can be put back in an airworthy condition. Any
substitutions or changes to procedures or tests identified as RC
require approval of an AMOC.

(l) Related Information

(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2015-0214, dated October 19, 2015, for related
information. This MCAI may be found in the AD docket on the Internet
at https://www.regulations.gov by searching for and locating Docket
No. FAA-2016-8849.
(2) For more information about this AD, contact Vladimir
Ulyanov, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton,
WA 98057-3356; telephone: 425-227-1138; fax: 425-227-1149.
(3) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (m)(3) and (m)(4) of this AD.

(m) Material Incorporated by Reference

(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(i) Airbus Service Bulletin A330-71-3028, Revision 02, dated
August 31, 2015.
(ii) Reserved.
(3) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.com.
(4) You may view this service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For
information on the availability of this material at the FAA, call
425-227-1221.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to https://www.archives.gov/federal-register/cfr/ibr-locations.html.

Issued in Renton, Washington, on May 8, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-10282 Filed 5-24-17; 8:45 am]
BILLING CODE 4910-13-P

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